Vehicle control systems and corresponding sizing methods
First Claim
1. A method for making a portion of an aircraft control system, comprising:
- selecting an actuator mechanism rate capability and an actuator mechanism load capability;
selecting at least one operating requirement;
determining the number and size of a plurality of control surfaces that are required to satisfy the at least one operating requirement during operation in an adjacent flow field so that, in response to at least one command signal, each control surface is actively positioned by one or more actuator mechanisms having the actuator mechanism rate capability and the actuator mechanism load capability; and
installing the control surfaces side by side along at least approximately an entire span of a trailing edge of an aircraft wing from a first trailing edge tip of the wing to a second trailing edge tip of the wing.
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Accused Products
Abstract
Vehicle control systems and methods for sizing such systems are disclosed. In one embodiment of the invention, an actuator mechanism capability is selected, at least one operating requirement is selected, and the required number, size, and locations of a plurality of control surfaces needed to satisfy the at least one operating requirement are determined. In another embodiment, a set of control laws is selected, at least one operating requirement is selected, and the number size, and location of a plurality of control surfaces needed to satisfy the at least one operating requirement are determined.
110 Citations
43 Claims
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1. A method for making a portion of an aircraft control system, comprising:
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selecting an actuator mechanism rate capability and an actuator mechanism load capability;
selecting at least one operating requirement;
determining the number and size of a plurality of control surfaces that are required to satisfy the at least one operating requirement during operation in an adjacent flow field so that, in response to at least one command signal, each control surface is actively positioned by one or more actuator mechanisms having the actuator mechanism rate capability and the actuator mechanism load capability; and
installing the control surfaces side by side along at least approximately an entire span of a trailing edge of an aircraft wing from a first trailing edge tip of the wing to a second trailing edge tip of the wing. - View Dependent Claims (2, 3, 4, 5)
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6. A method for sizing at least a portion of a vehicle control system, comprising:
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selecting an actuator mechanism capability;
selecting at least one operating requirement; and
determining the number and size of a plurality of control surfaces that are required to satisfy the at least one operating requirement during operation in an adjacent flow field so that, in response to at least one command signal, each control surface is actively positioned by at least one actuator mechanism having the actuator mechanism capability. - View Dependent Claims (7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21)
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22. A method for sizing a vehicle control system, comprising:
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selecting a set of control laws;
selecting at least one operating requirement; and
determining the number and size of a plurality of control surfaces that are required to satisfy the at least one operating requirement during operation in an adjacent flow field so that, in response to at least one command signal that is governed, at least in part, by the set of control laws, each control surface is actively positioned by an actuator mechanism having the actuator mechanism capability. - View Dependent Claims (23, 24, 25, 26, 27)
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28. A portion of a vehicle control system, comprising:
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at least one external fluid flow body having a forward portion with a first flow surface, a second flow surface facing opposite the first flow surface, and a trailing edge at a juncture of the first flow surface and the second flow surface, the trailing edge having a span extending from a first trailing edge tip to a second trailing edge tip;
a plurality of control surfaces, each having at least a portion aft of the trailing edge of the external fluid flow body, the control surfaces being movable relative to the at least one external fluid flow body to control forces and moments on the external fluid flow body by interacting with an adjacent flow field; and
a plurality of actuator mechanisms, each having an approximately identical control capability, at least one actuator mechanism being coupled to each of the control surfaces to actively position the control surfaces in response to command signals. - View Dependent Claims (29, 30, 31, 32, 33, 34, 35, 36, 37, 38, 39, 40)
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41. An aircraft, comprising:
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a fuselage;
a forward wing portion, the forward wing portion having a leading edge and a trailing edge, the trailing edge of the forward wing portion having a span extending from a first trailing edge tip to a second trailing edge tip;
a plurality of control surfaces, each having at least a portion positioned aft of the trailing edge, the control surfaces being distributed across at least approximately the entire span of the trailing edge, the control surfaces being movable relative to the forward wing portion to control forces and moments on the forward wing portion by interacting with an adjacent flow field; and
a plurality of actuator mechanisms, each having an approximately identical control capability, each actuator mechanism being coupled to a control surface to actively position the corresponding control surface in response to command signals. - View Dependent Claims (42, 43)
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Specification